System and method for limiting movement of a retaining ring

ABSTRACT

A method of installing a retaining ring assembly in a turbine case is provided. The method may include installing a blade outer air seal into a case before installation of a retaining ring assembly. The method may further include installing a key system on a retaining ring to create the retaining ring assembly. The method may also include installing the retaining ring assembly in a case. The method may further include rotating the retaining ring assembly in the case until key system is aligned with a case slot. The method may also include tightening the key system to the retaining ring and cause key system to engage the case slot.

FIELD

The present disclosure relates systems and methods for limiting themovement of a retaining ring, and more particularly, a key system and acorresponding method of installation for a retaining ring in a gasturbine engine.

BACKGROUND

In typical retaining ring installations, adjacent structures are used toradially retain retaining rings. In this regard, in a typicallyinstallation, the retaining ring would be captured by one or more,clips, fasteners, or parts and held radially against the staticstructure of the aircraft. However, where no adjacent static structureis available, a system and method of installation are needed to hold theretaining ring.

SUMMARY

A method of installing a retaining ring assembly in a turbine case maybe provided. The method may include installing a blade outer air sealsupport into a case before installation of a retaining ring assembly.The method may further include installing a key system on a retainingring to create the retaining ring assembly. The method may also includeinstalling the retaining ring assembly in a case. The method may furtherinclude rotating the retaining ring assembly in the case until keysystem may be aligned with a case slot. The method may also includetightening the key system to the retaining ring and cause key system toengage the case slot.

In various embodiments, the key system may comprise a key washer. Thekey system may further comprise a fastener and a nut. The key washer mayhave a shape that corresponds to the case slot. The fastener may mountflush in a first side of the retaining ring. The fastener may protrudethrough second side of the retaining ring to engage the key washer andreceive the nut. In this regard, the fastener may be installable throughthe retaining ring to mount the key washer to the retaining ring.

In various embodiments, the engagement of the case slot may beconfigured to restrain circumferential motion of the retaining ringassembly. The key washer may have a shape that corresponds to the caseslot.

In various embodiments, the BOAS support may comprise a support tab. Theretaining ring may also comprise a tab. The tab of the retaining ringmay be aligned with the support tab in response to the sliding of theretaining ring. In various embodiments, the support tab may beconfigured to restrain radial motion of the retaining ring assembly.

In various embodiments, a retaining ring assembly may comprise aretaining ring, a fastener, a key washer, and a nut. The fastener may beinstallable through the retaining ring. The key washer may beinstallable on the fastener. The nut may be installable on the fastener.The nut may be configured to tighten the key washer to the retainingring.

In various embodiments, the retaining ring may be installable in a highpressure turbine case.

In various embodiments, the retaining ring may further comprise support.The support may be configured to engage a blade outer air seal supporttab.

In various embodiments, the key washer may restrain circumferentialmovement of retaining ring assembly in response to the retaining ringbeing installed in the high pressure turbine case. The BOAS support tabmay restrain radial movement of the retaining ring assembly in responseto the retaining ring being installed in the high pressure turbine case.

In various embodiments, gas turbine engine may comprise a compressor, acombustor, a turbine, and a retaining ring assembly. The combustor maybe in fluid communication with the compressor. The turbine may be influid communication with the combustor. The retaining ring assembly maybe installable in a turbine case. The retaining ring assembly maycomprise a retaining ring, a fastener, a key washer and a nut. Thefastener may be installable through the retaining ring. The key washermay be installable on the fastener. The nut may be installable on thefastener. The nut may be configured to tighten the key washer to theretaining ring. The nut may cause the key washer to engage the turbinecase.

In various embodiments, the key washer may restrain circumferentialmovement of the retaining ring assembly in response to the retainingring being installed in the high pressure turbine case. In variousembodiments, the retaining ring may further comprise a support that maybe configured to engage a blade outer air seal support tab. The BOASsupport tab may restrain radial movement of the retaining ring assemblyin response to the retaining ring being installed in the high pressureturbine case.

The forgoing features and elements may be combined in variouscombinations without exclusivity, unless expressly indicated hereinotherwise. These features and elements as well as the operation of thedisclosed embodiments will become more apparent in light of thefollowing description and accompanying drawings.

BRIEF DESCRIPTION OF THE DRAWINGS

The subject matter of the present disclosure is particularly pointed outand distinctly claimed in the concluding portion of the specification. Amore complete understanding of the present disclosure, however, may bestbe obtained by referring to the detailed description and claims whenconsidered in connection with the drawing figures, wherein like numeralsdenote like elements.

FIG. 1 illustrates a cross-sectional view of an exemplary gas turbineengine, in accordance with various embodiments;

FIG. 2A illustrates a perspective view of a portion of the high pressureturbine, in accordance with various embodiments;

FIG. 2B illustrates a perspective view of a portion of the high pressureturbine, in accordance with various embodiments;

FIG. 2C illustrates a cross-sectional view of retaining ring installedin a high pressure turbine case at a first circumferential location, inaccordance with various embodiments;

FIG. 2D illustrates a cross-sectional view of retaining ring installedin a high pressure turbine case at a second circumferential location, inaccordance with various embodiments;

FIG. 2E illustrates a cross-sectional view of retaining ring installedin a high pressure turbine case at a third circumferential location, inaccordance with various embodiments; and

FIG. 3 is an installation process for a retaining ring, in accordancewith various embodiments.

DETAILED DESCRIPTION

The detailed description of exemplary embodiments herein makes referenceto the accompanying drawings, which show exemplary embodiments by way ofillustration. While these exemplary embodiments are described insufficient detail to enable those skilled in the art to practice theseembodiments, it should be understood that other embodiments may berealized and that logical changes and adaptations in design andconstruction may be made in accordance with the present disclosure andthe teachings herein. Thus, the detailed description herein is presentedfor purposes of illustration only and not for providing limitations onthe scope of the disclosure. For example, the steps recited in any ofthe methods or process descriptions may be executed in any order and arenot limited to the order presented. Furthermore, any reference tosingular includes plural embodiments, and any reference to more than onecomponent or step may include a singular embodiment or step. Also, anyreference to attached, fixed, connected or the like may includepermanent, removable, temporary, partial, full and/or any other possibleattachment option. Additionally, any reference to without contact (orsimilar phrases) may also include reduced contact or minimal contact.Moreover, surface shading lines may be used throughout the figures todenote different parts but not necessarily to denote the same ordifferent materials.

In various embodiments and with reference to FIG. 1, a gas turbineengine 120 is provided. Gas turbine engine 120 may be a two-spoolturbofan that generally incorporates a fan section 122, a compressorsection 124, a combustor section 126 and a turbine section 128.Alternative engines may include, for example, an augmentor section amongother systems or features. In operation, fan section 122 can drive airalong a bypass flow-path B while compressor section 124 can drive airalong a core flow-path C for compression and communication intocombustor section 126 then expansion through turbine section 128.Although depicted as a turbofan gas turbine engine 120 herein, it shouldbe understood that the concepts described herein are not limited to usewith turbofans as the teachings may be applied to other types of turbineengines including three-spool architectures.

Gas turbine engine 120 may generally comprise a low speed spool 130 anda high speed spool 132 mounted for rotation about an engine centrallongitudinal axis A-A′ relative to an engine static structure 136 viaone or more bearing systems 138 (shown as bearing system 138-1 andbearing system 138-2 in FIG. 1). It should be understood that variousbearing systems 138 at various locations may alternatively oradditionally be provided including, for example, bearing system 138,bearing system 138-1, and bearing system 138-2.

Low speed spool 130 may generally comprise an inner shaft 140 thatinterconnects a fan 142, a low pressure (or first) compressor section144 and a low pressure (or first) turbine section 146. Inner shaft 140may be connected to fan 142 through a geared architecture 148 that candrive fan 142 at a lower speed than low speed spool 130. Gearedarchitecture 148 may comprise a gear assembly 160 enclosed within a gearhousing 162. Gear assembly 160 couples inner shaft 140 to a rotating fanstructure. High speed spool 132 may comprise an outer shaft 150 thatinterconnects a high pressure compressor (“HPC”) 152 (e.g., a secondcompressor section) and high pressure (or second) turbine section 154. Acombustor 156 may be located between HPC 152 and high pressure turbine154. A mid-turbine frame 157 of engine static structure 136 may belocated generally between high pressure turbine 154 and low pressureturbine 146. Mid-turbine frame 157 may support one or more bearingsystems 138 in turbine section 128. Inner shaft 140 and outer shaft 150may be concentric and rotate via bearing systems 138 about the enginecentral longitudinal axis A-A′, which is collinear with theirlongitudinal axes. As used herein, a “high pressure” compressor orturbine experiences a higher pressure than a corresponding “lowpressure” compressor or turbine.

The core airflow C may be compressed by low pressure compressor 144 thenHPC 152, mixed and burned with fuel in combustor 156, then expanded overhigh pressure turbine 154 and low pressure turbine 146. Mid-turbineframe 157 includes airfoils 159 which are in the core airflow path. Lowpressure turbine 146 and high pressure turbine 154 rotationally drivethe respective low speed spool 130 and high speed spool 132 in responseto the expansion.

Gas turbine engine 120 may be, for example, a high-bypass gearedaircraft engine. In various embodiments, the bypass ratio of gas turbineengine 120 may be greater than about six (6). In various embodiments,the bypass ratio of gas turbine engine 120 may be greater than ten (10).In various embodiments, geared architecture 148 may be an epicyclic geartrain, such as a star gear system (sun gear in meshing engagement with aplurality of star gears supported by a carrier and in meshing engagementwith a ring gear) or other gear system. Geared architecture 148 may havea gear reduction ratio of greater than about 2.3 and low pressureturbine 146 may have a pressure ratio that is greater than about 5. Invarious embodiments, the bypass ratio of gas turbine engine 120 isgreater than about ten (10:1). In various embodiments, the diameter offan 142 may be significantly larger than that of the low pressurecompressor 144, and the low pressure turbine 146 may have a pressureratio that is greater than about 5:1. Low pressure turbine 146 pressureratio may be measured prior to inlet of low pressure turbine 146 asrelated to the pressure at the outlet of low pressure turbine 146 priorto an exhaust nozzle. It should be understood, however, that the aboveparameters are exemplary of various embodiments of a suitable gearedarchitecture engine and that the present disclosure contemplates othergas turbine engines including direct drive turbofans.

In various embodiments, blade outer error seals (“BOAS”) are installedin the high pressure turbine. The BOAS may be held in place by a supportsegment and a retaining ring. During maintenance of the hot section ofthe engine and/or the turbine section of the engine, the BOAS may beremoved and serviced or replaced. Moreover the corresponding supportstructures and retaining wings may need to be removed and replaced.These support structures and retaining rings will also benefit frombeing held in place and/or secured so that the structures do not moveand/or become free in the engine when the engine is operating.

In various embodiments and with reference to FIGS. 2A through 2E,turbine section 128 and/or case 129 (e.g., turbine case 129) maycomprise and/or may be configured to receive a retaining ring 190.Retaining ring 190 may be configured to retain, support, secure and/orotherwise hold a BOAS support structure 149 and/or a BOAS correspondingto a turbine blade of turbine section 128. Retaining ring 190 may beinstallable within slot 181. Slot 181 may be defined in case 129.

If left unrestrained, retaining ring 190 may freely spin within slot181. The movement of retaining ring 190 may increase during engineoperation when the engine is vibrating. This movement may cause wearand/or stress on retaining ring 190.

In various embodiments, retaining ring 190 may be supported by BOASsupport structure 149. The BOAS support structure 149 may comprise oneor more support tabs 180 formed on a portion of BOAS support structure149. Retaining ring 190 may comprise one or more supports 192 (e.g.,tab). Support 192 may be alignable with support tab 180. In this regard,support 192 is radially supported by support tab 180, minimizing themovement of retaining ring in a radio fashion relative to the centerlineof A-A of engine 120 as shown in FIG. 1, retaining ring 190 may furtherbe engagable by a key system 170 (e.g., key system 170 may be tightenedagainst retaining ring 190).

In various embodiments, key system 170 may comprise a key 172 (e.g., akey washer) and a fastener system 175. Fastener system 175 may compriseany suitable fastener 174 and any suitable fastener retainer 176. Forexample, fastener 174 may be a screw, threaded shaft, bolt, and/or thelike. Fastener retainer 176 may be a nut or any other suitabletightening device that is configured to engage fastener 174. In thisregard, fastener system 175 may be configured to engage and retain key172 against retaining ring 190.

In various embodiments, one or more keys 172 of key system 170 may beconfigured to engage one or more case slots 184 defined in case 129. Inthis regard, key 172 may have a shape that corresponds to the shape ofcase slot 184. The shape of key 172 may be complimentary to the shape ofcase slot 184 to insure a proper fit (e.g., a tight fit to minimizemovement of retaining ring 190). One or more case slot 184 may bepositioned at specific positions allowing retaining ring to be rotatedand clocked at a particular position. This may allow retaining ring 190and, more specifically, support 192 to align with support tab 180.

In various embodiments, the engagement between key 172 and case slot 184may also limit and/or restrain the circumferential motion of retainingring 190 circumferential motion within slot 181. The engagement betweensupport 192 and support tab 180 may also limit and/or restrain theradial motion of retaining ring 190 within slot 181.

In various embodiments, retaining ring 190 may comprise one or moresupports 192. Similarly, BOAS support structure 149 may comprise one ormore corresponding support tabs 180. Retaining ring 190 may also beconfigured to receive one or more keys 172. Case 129 may comprise one ormore corresponding case slots 184.

In various embodiments and with reference to FIG. 2A through FIG. 3, amethod 300 for installing a retaining ring in a turbine case isprovided. Method 300 may include installing BOAS support structure 149into a case before installation of retaining ring assembly 195 (Step310). Method 300 may further include installing key system 170 onretaining ring 190 to create the retaining ring assembly 195 (Step 320).In response to creating clearance for the retaining ring assembly 195,method 300 may further include installing retaining ring assembly 195 incase 129 (step 330). More specifically, retaining ring assembly 195 maybe installed in slot 181 of case 129. Moreover, retaining ring assembly195 may be installed in slot 181 such that it is allowed to movecircumferentially within the case. Method 300 may further includerotating retaining ring assembly 195 in case 129 until key 172 isaligned with case slot 184 (step 340). Based on the sliding of theretaining ring within slot 181, one or more supports 192 may align withone or more support tabs 180. Method 300 may further include engagingfastener system 175 to tighten key 172 to retaining ring 190 and causekey 172 to engage case slot 184 (step 350). The engagement of case slot184 by key 172 may limit the circumferential motion of retaining ring190 within slot 181. Moreover, the appropriate clocking of retainingring 190 and the engagement of support 192 at support tab 180 may limitand/or restrain any radial motion of retaining ring 190.

Benefits and advantages have been described herein with regard tospecific embodiments. Furthermore, the connecting lines shown in thevarious figures contained herein are intended to represent exemplaryfunctional relationships and/or physical couplings between the variouselements. It should be noted that many alternative or additionalfunctional relationships or physical connections may be present in apractical system. However, such benefits, advantages, and any elementsthat may cause any benefit or advantage to occur or become morepronounced are not to be construed as critical, required, or essentialfeatures or elements of the disclosure. Reference to an element in thesingular is not intended to mean “one and only one” unless explicitly sostated, but rather “one or more.” Moreover, where a phrase similar to“at least one of A, B, or C” is used in the claims, it is intended thatthe phrase be interpreted to mean that A alone may be present in anembodiment, B alone may be present in an embodiment, C alone may bepresent in an embodiment, or that any combination of the elements A, Band C may be present in a single embodiment; for example, A and B, A andC, B and C, or A and B and C.

Systems, methods and apparatus are provided herein. In the detaileddescription herein, references to “various embodiments”, “oneembodiment”, “an embodiment”, “an example embodiment”, etc., indicatethat the embodiment described may include a particular feature,structure, or characteristic, but every embodiment may not necessarilyinclude the particular feature, structure, or characteristic. Moreover,such phrases are not necessarily referring to the same embodiment.Further, when a particular feature, structure, or characteristic isdescribed in connection with an embodiment, it is submitted that it iswithin the knowledge of one skilled in the art to affect such feature,structure, or characteristic in connection with other embodimentswhether or not explicitly described. After reading the description, itwill be apparent to one skilled in the relevant art(s) how to implementthe disclosure in alternative embodiments.

Furthermore, no element, component, or method step in the presentdisclosure is intended to be dedicated to the public regardless ofwhether the element, component, or method step is explicitly recited inthe claims. No claim element herein is to be construed under theprovisions of 35 U.S.C. 112(f), unless the element is expressly recitedusing the phrase “means for.” As used herein, the terms “comprises”,“comprising”, or any other variation thereof, are intended to cover anon-exclusive inclusion, such that a process, method, article, orapparatus that comprises a list of elements does not include only thoseelements but may include other elements not expressly listed or inherentto such process, method, article, or apparatus.

What is claimed is:
 1. A method, comprising: install a blade outer airseal (“BOAS”) support into a case before installation of a retainingring assembly; install a key system on a retaining ring to create theretaining ring assembly; install the retaining ring assembly in thecase; rotate the retaining ring assembly in the case until key system isaligned with a case slot; and tighten the key system to the retainingring and cause key system to engage the case slot.
 2. The method ofclaim 1, wherein the key system comprises a key washer.
 3. The method ofclaim 2, wherein the key system further comprises a fastener and a nut.4. The method of claim 3, wherein the key washer has a shape thatcorresponds to the case slot.
 5. The method of claim 4, wherein thefastener mounts flush in a first side of the retaining ring andprotrudes through second side of the retaining ring to engage the keywasher and receive the nut.
 6. The method of claim 3, wherein thefastener is installable through the retaining ring to mount the keywasher to the retaining ring.
 7. The method of claim 6, wherein theengagement of the case slot is configured to restrain circumferentialmotion of the retaining ring assembly.
 8. The method of claim 1, whereinthe BOAS support comprises a support tab.
 9. The method of claim 8,wherein the retaining ring comprises a support.
 10. The method of claim9, wherein the support of the retaining ring is aligned with the supporttab in response to the sliding of the retaining ring.
 11. The method ofclaim 10, wherein the support tab is configured to restrain radialmotion of the retaining ring assembly.
 12. The method of claim 2,wherein the key washer has a shape that corresponds to the case slot.13. A retaining ring assembly, comprising, a retaining ring; a fastenerinstallable through the retaining ring; a key washer installable on thefastener; and a nut installable on the fastener and configured totighten the key washer to the retaining ring.
 14. The retaining ringassembly of claim 13, the retaining ring installable in a high pressureturbine case.
 15. The retaining ring assembly of claim 14, the retainingring further comprising support that is configured to engage a bladeouter air seal support tab.
 16. The retaining ring assembly of claim 15,wherein the key washer restrains circumferential movement and thesupport restrains radial movement of the retaining ring of the retainingring assembly in response to the retaining ring being installed in thehigh pressure turbine case.
 17. A gas turbine engine, comprising: acompressor; a combustor in fluid communication with the compressor; aturbine in fluid communication with the combustor; a retaining ringassembly installable in a turbine case, the retaining ring assemblycomprising, a retaining ring; a fastener installable through theretaining ring; a key washer installable on the fastener; and a nutinstallable on the fastener and configured to tighten the key washer tothe retaining ring and cause the key washer to engage the turbine case.18. The gas turbine engine of claim 17, wherein the key washer restrainscircumferential movement of the retaining ring assembly in response tothe retaining ring being installed in a high pressure turbine case. 19.The gas turbine engine of claim 17, the retaining ring furthercomprising a support that is configured to engage a blade outer air sealsupport tab.
 20. The gas turbine engine of claim 19, wherein the supportrestrains radial movement of the retaining ring of the retaining ringassembly in response to the retaining ring being installed in a highpressure turbine case.